Thermoacoustic loads and fatigue of hypersonic vehicle skin panels

Blevins, Robert D.; Holehouse, I.; Wentz, Kenneth R.

doi:10.2514/3.46441

Cited by 117 publications

(101 citation statements)

References 5 publications

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“…In addition, with advanced stealth technology, stores are being located internally, which is presenting a new problem in the form of cavity noise and the high intensity loads which are being experienced within the bays that house the stores of these aircraft. In conjunction with higher sound pressure levels, recent developments in acoustic fatigue research have also concentrated on combined thermal-acoustic environments, which are being driven by studies of possible hypersonic vehicle designs [20,21]. Green and Killey [22] highlighted the fact that the current adopted method of using linear vibration theory for determinig fatigue life, which assumes that the pressure field is fully correlated over the surface area of the structure, becomes increasingly unsatisfactory when geometric non-linearities occur due to high sound pressure levels.…”

Section: Prediction and Measurement Of The Non-linear Response Due Tomentioning

confidence: 99%

A review of analytical methods for aircraft structures subjected to high-intensity random acoustic loads

Cunningham

White

2004

Proceedings of the Institution of Mechanical Engineers, Part G:

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A review of the acoustic fatigue design process for aircraft structures is presented in this paper, together with the current design guides, which are used to predict the stresses that an acousticallly loaded aircraft structure may experience in service. These methods are based on linear theory and use the single-degree-of-freedom approximation method. A recent programme of research which uses this method together with the finite element method to predict the root mean square strains experienced by acoustically excited, doubly curved sandwich panels is briefly discussed. Recent developments in prediction methods based on the non-linear dynamic response of thermoacoustic loaded structures are reviewed, and suggestions are made as to possible future directions in the area of acoustic fatigue research.

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Section: Prediction and Measurement Of The Non-linear Response Due Tomentioning

confidence: 99%

A review of analytical methods for aircraft structures subjected to high-intensity random acoustic loads

Cunningham

White

2004

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…But it can be explored form many thermal structure tests that high acoustic and thermal loading are interdependent [3], this phenomenon is recognized as a challenge for tests. After aerothermoelastic analysis of aircraft in hypersonic flow, thermoacoustic loads and fatigue of the skin panel of hypersonic vehicles have been investigated by Blevins and Holehouse [4]; Yu et al [5,6] recently proposed a method including a control-oriented dynamic model for simulate the sound-heatfluid coupling problem in a reverberation room and discussed the effect of decoupling the multi-physics fields. In addition, Li discussed a numerical method to simulate sound transmission from air to flow through plates [7], this work presented a basis for the sound-fluid-structure coupling.…”

Section: Introductionmentioning

confidence: 99%

Numerical Analysis of Thermoacoustic Characteristics of Components inside a Complex Aircraft Related to the Coupling Effect of High Temperature and Random Vibration

Bai

Zhao

Xia

et al. 2015

Journal of Low Frequency Noise, Vibration and Active Control

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Hypersonic aircraft always face bad flight environment related to the coupling effects of high temperature and random vibration. Numerical analysis of thermoacoustic characteristics of components inside such an aircraft is presented in this paper. An actual aircraft cabin composite structure including a heat resistant layer, an adiabatic layer and metal frameworks is modeled with the finite element mesh generation method. Transient heat conduction of the hypersonic flight aircraft is analyzed based on a block-iterative coupling method which can consider the atmosphere-aircraft interaction. Then the Von Karman turbulence spectrum is employed to define the random vibration environment of the present aircraft. The thermodynamic response of the system is solved by the pseudo-excitation method which can improve the computation efficiency greatly. Finally, thermoacoustic characteristic of the cavity inside the aircraft cabin is analyzed when the transient heat conduction and random vibration due to atmosphere turbulence are both included. A numerical method is proposed based on a structure-acoustic coupling method which can use acoustic equations to simulate the propagation of the acoustic wave in the flow. It can be found from the computed results that the change of the temperature influences both the thermodynamic characteristic of the aircraft cabin and thermoacoustic characteristic of the component inside the present aircraft significantly. So the coupling effects of high temperature and random vibration on thermoacoustic characteristic of a hypersonic flight aircraft cannot be neglected. The proposed numerical analysis method in this paper can be widely applied to numerical investigations of thermoacoustic systems inside hypersonic aircraft.

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“…In the strength analysis of ceramic thermal insulation tile, special attention should be paid to the pneumatic and acoustic vibration of the thermal insulation tile system. Dynamic strength problem under the combined action of substrate deformation [10][11][12]. Due to the great difference in elastic modulus between ceramic insulating tile and strain isolating pad, the deformation of the structure is mainly concentrated on the strain-isolating pad with lower modulus.…”

Section: Introductionmentioning

confidence: 99%

Vibration characteristics of thermal insulation tile with material and geometric nonlinear effects

Zhao

Xia

Shen

2018

IOP Conf. Ser.: Mater. Sci. Eng.

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The effect of temperature, static load and electron beam irradiation on the deformation of linear polymers A I Kupchishin, M N Niyazov, N A Voronova et al. -Multiscale nonlinear frequency response analysis of single-layered graphene sheet under impulse and harmonic excitation using the atomistic finite element method Sachin O Gajbhiye and S P Singh Abstract. Thermal protection system (TPS) composed of ceramic insulation tile and strain-isolation pad (SIP) tends to be destroyed by excessive inner strain arises from aerodynamic load or substructure deformation/vibration. Both material nonlinearity and geometric nonlinearity affect the static and dynamic strength of TPS, and the nonlinear effects of SIP need to be considered in the strength analysis. By considering both the material nonlinearity and geometric nonlinearity of SIP, the effect of external static load on the dynamic characteristics of tile-SIP system is investigated. Firstly, a theoretical model is established to calculate the natural frequency of tiles under static load with material and geometric nonlinearities. The analysis procedure is separated into two steps. The first step is the nonlinear analysis to determine the static large deformation. The second step is the linearized dynamic analysis on the base of static deformation with small vibration amplitude assumption. The complexity is reduced by introducing a nonlinear coefficient parameter. The theoretical results have good agreement with COMSOL simulation. Numerical results show that large deformation is found in the flexible SIP when uniform static load applied on the surface of the tile, which introduces significant material and geometric nonlinearities and changes the dynamic characteristics of the tile. 9% increase of intrinsic frequency is found for the static load of 80kPa when considering material nonlinearity, while 16% increase of intrinsic frequency is found when considering both material and geometric nonlinearities. It is concluded that the uniform static load has important effect on the nature frequency of tile-SIP systems when introducing the material and geometric nonlinearities into the calculation. The nonlinearities of the SIP need to be considered in the tile-SIP dynamic strength analysis.

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Thermoacoustic loads and fatigue of hypersonic vehicle skin panels

Cited by 117 publications

References 5 publications

A review of analytical methods for aircraft structures subjected to high-intensity random acoustic loads

A review of analytical methods for aircraft structures subjected to high-intensity random acoustic loads

Numerical Analysis of Thermoacoustic Characteristics of Components inside a Complex Aircraft Related to the Coupling Effect of High Temperature and Random Vibration

Vibration characteristics of thermal insulation tile with material and geometric nonlinear effects

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